一种飞艇尾翼与气囊装配位置确定方法
By measuring the actual and theoretical dimensions of the tail fin root rib and calculating the scaling ratio, a scaled-up root rib template was cut out using a flexible composite material template. This solved the problem of misalignment between the tail fin and the airbag assembly position and achieved a precise assembly effect.
CN117755514BActive Publication Date: 2026-07-17CHINA SPECIAL TYPE FLIER RES INST
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- CHINA SPECIAL TYPE FLIER RES INST
- Filing Date
- 2023-12-29
- Publication Date
- 2026-07-17
AI Technical Summary
Technical Problem
The assembly position of the airship's tail fin and airbag was offset due to machining errors and material shrinkage during heat sealing, resulting in non-compliance with assembly requirements.
Method used
By measuring the actual and theoretical dimensions of the tail fin root rib, calculating the scaling ratio, cutting out the scaled root rib template using a flexible composite material template, and drawing the tail fin and bulkhead position lines on the airbag cut piece to ensure precise assembly.
Benefits of technology
This reduces the assembly error between the tail fin and the airbag, improving the effectiveness and precision of the assembly.
✦ Generated by Eureka AI based on patent content.
Smart Images
Figure CN117755514B_ABST
Abstract
本发明属于浮空器制造技术领域，公开了一种飞艇尾翼与气囊装配位置确定方法，包括以下步骤：步骤一：准备试验环境；步骤二：对尾翼根肋的成品实际尺寸进行测量；步骤三：对尾翼根肋的理论尺寸进行测量；步骤四：根据尾翼根肋的成品实际尺寸和理论尺寸确定尾翼根肋的缩放比例，并根据缩放比例绘制缩放后的实际根肋裁片图；步骤五：根据实际根肋裁片图，裁剪缩放后的根肋模板；步骤六：利用根肋模板在气囊裁片上确定尾翼根肋的安装位置并装配尾翼根肋。
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